IT IS THE INTENTION OF AUBURN UNIVERSITY COMBUSTION PHYSICS LAB TO DEMONSTRATE SIMULTANEOUSLY INTEGRATED METHANE RICH AND OXYGEN RICH PRE-BURNERS WITH CONTINUOUS DETONATION ENGINES (CDES). THIS WOULD BE AN INAUGURAL STEP TOWARDS ROCKET ENGINE POWER CYCLE INTEGRATION. IDEALIZED FLIGHT VEHICLES REQUIRE HIGH PRESSURE RATIO NOZZLES TO MAXIMIZE ENGINE THRUST PRODUCTION. TURBOMACHINERY WILL BE NEEDED TO DRIVE PUMPS TO MEET THESE PRESSURE DEMANDS. THE MOST EFFICIENT MEANS OF DELIVERING POWER TO THIS TURBOMACHINERY IS THROUGH PRE-BURNERS. PRE-BURNERS EXTRACT CHEMICAL POTENTIAL ENERGY WITHIN THE PROPELLANT TO DRIVE TURBOMACHINERY. THE LOW TEMPERATURE BURNING OF THE PROPELLANT THROUGH THE PREBURNERS RELEASES SMALL QUANTITIES OF THE PROPELLANT S CHEMICAL POTENTIAL ENERGY. THIS IS RELEASED AS HEAT AND PRESSURIZATION OF THE PROPELLANT FLOW. THIS ENERGY RELEASE CAN THEN BE CAPTURED WITHIN THE POWER CYCLE SYSTEM AND CONVERTED INTO MECHANICAL WORK. THIS ENABLES THE MAXIMUM EXTRACTION OF USEFUL WORK FROM THE PROPELLANTS.